Problem Description

The problem considers the flow around an airfoil at an angle of attack $\alpha = 4^{\circ}$ and a free stream Mach number of $0.8$ ( $M_{\infty} = 0.8$). The flow is transonic, and has a fairly strong shock near the mid-chord ( $x/c = 0.45$) on the upper (suction) side. The chord length is 1 m. The geometry of the airfoil is shown in Figure  3.1.

Figure 3.1: Problem Specification